Gas turbine engine combustor with lobed, three dimensional contouring

Abstract

A gas turbine engine combustor is provided and includes an array of fuel nozzles, a combustion casing assembly disposed about the array of fuel nozzles and an end cap assembly disposed within the combustion casing assembly to define with the combustion casing assembly an axis-symmetric annulus through which fluid travels into each of the fuel nozzles, at least one of the combustion casing assembly and the end cap assembly being formed with lobed, three-dimensional contouring.

The invention claimed is: 
     
       1. A gas turbine engine combustor, comprising:
 an array of fuel nozzles including a central fuel nozzle and outer fuel nozzles spaced about the central fuel nozzle; 
 a combustion casing assembly disposed about the array of fuel nozzles; and 
 an end cap assembly disposed within the combustion casing assembly to define with the combustion casing assembly an axis-symmetric annulus through which fluid travels into each of the fuel nozzles, 
 the combustion casing assembly and the end cap assembly being formed with lobed, three-dimensional contouring relating to each of the outer fuel nozzles and extending radially inwardly between adjacent outer fuel nozzles to a perimeter of the central fuel nozzle. 
 
     
     
       2. The gas turbine engine combustor according to  claim 1 , wherein the fluid comprises compressor discharge feed air. 
     
     
       3. The gas turbine engine combustor according to  claim 1 , wherein the axis-symmetric annulus directs the fluid to flow in a first direction, radially inwardly and then in a second direction opposite the first direction. 
     
     
       4. The gas turbine engine combustor according to  claim 1 , wherein the combustion casing assembly comprises:
 a casing barrel that extends axially and has an annular shape in which the array of fuel nozzles is disposed; 
 a forward flange at a forward end of the casing barrel; and 
 an aft flange at an aft end of the casing barrel, wherein the lobed, three-dimensional contouring of the combustion casing assembly comprises a scallop structure provided at least on the casing barrel and/or the forward flange. 
 
     
     
       5. The gas turbine engine combustor according to  claim 4 , wherein adjacent scallop structures define a groove portion. 
     
     
       6. The gas turbine engine combustor according to  claim 4 , wherein the end cap assembly comprises:
 an end cap baffle; and 
 a turning plate at a forward end of the end cap baffle, wherein the lobed, three dimensional contouring of the end cap assembly comprises a scallop structure provided at least one the end cap baffle and/or the turning plate. 
 
     
     
       7. The gas turbine engine combustor according to  claim 6 , wherein adjacent scallop structures form a rim portion. 
     
     
       8. The gas turbine engine combustor according to  claim 1 , wherein the array of fuel nozzles comprises:
 the central fuel nozzle; and 
 five outer fuel nozzles substantially uniformly spaced about the central fuel nozzle. 
 
     
     
       9. The gas turbine engine combustor according to  claim 1 , wherein each of the fuel nozzles comprises a flange formed with lobed, three-dimensional contouring. 
     
     
       10. The gas turbine engine combustor according to  claim 9 , wherein the flange of each of the fuel nozzles connects with the end cap assembly. 
     
     
       11. The gas turbine engine combustor according to  claim 1 , wherein the lobed, three-dimensional contouring of the combustion casing assembly and the end cap assembly are circumferentially aligned. 
     
     
       12. The gas turbine engine combustor according to  claim 1 , wherein the lobed, three-dimensional contouring of the combustion casing assembly and the end cap assembly are radially aligned. 
     
     
       13. A gas turbine engine combustor, comprising:
 a central fuel nozzle; 
 a plurality of outer fuel nozzles arrayed substantially uniformly about the central fuel nozzle; 
 a combustion casing assembly disposed about the array of outer fuel nozzles; and 
 an end cap assembly disposed within the combustion casing assembly to define with the combustion casing assembly an axis-symmetric annulus through which fluid travels into each of the fuel nozzles, 
 the combustion casing assembly and the end cap assembly being formed with lobed, three-dimensional contouring relating to each of the plurality of outer fuel nozzles. 
 
     
     
       14. A gas turbine engine combustor with a single component lobed insert, the gas turbine engine combustor comprising:
 a central fuel nozzle; 
 an array of fuel nozzles arrayed substantially uniformly about the central fuel nozzle; 
 an end cover; 
 a combustion casing assembly connected to the end cover and disposed about the array of fuel nozzles; 
 an end cap assembly disposed within the combustion casing assembly to define an axis-symmetric annulus through which fluid travels into each of the fuel nozzles; and 
 an insert connected to an aft face of the end cover within the combustion casing assembly, 
 the insert including a medallion shaped body having an aft face formed with lobed, three-dimensional contouring comprising scallop sections relating to each of the fuel nozzles and extending radially inwardly between adjacent outer fuel nozzles to a perimeter of the central fuel nozzle.